Controlling device for aeroplanes



C. R. FAIREY.

CONTROLLING DEVICE FOR AEROPLANES.

APPLICATION FILED APR.Z3. 1919.

Patented Aug. 17, 1920 3 SHEETS-SHEET 1.

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CONTROLLING DEVICE FOR AEROPLANES.

APP LICAT|0N man Amzs. 1919. 1 350, 1 45. Patented Aug. 17, 1920.v

3 sHEETsesHEET 2.

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CONTROLLING DEVICE FOR AEROPLANES.

APPLICATION FILED A PII.23. I9I-9.

Patented Aug. 17,1920.

- 3 SHEETS-SHEET a.

onrrso stares OFFICE.

ciiAnLEs RICHARD rn nntrfor HAYES, ENGLAND. i

" CONTROLLING DEVICE FOR AERoPL NEs.

To all whom it may V concern:

Be it known that 1,.Cr-mnnns1tro1mno Fnnmr, asubject of the King of Great llritain, and tormerlyresident of Clayton Road, Hayes, in the county of Middlesex, England, but now of (lranford. Lane,:Hayes, in the county of Middlesex, England, have invented a certain new and useful Improvement in and Relating to Controlling Devices for Aeroplanes, of which the follow ing is a specification.

'This invention. relates whereof the wings have trailing marginal portions, of :variable inclination, respectively provided witlr control cables and with mechanism for so actuating the same.

as to cause the cambers of the respective wings to be varied simultaneously either in reverse directions or in the same direction, at will, by positive action transmitted through a closed mechanical circuit, and the invention has for its primary objectto provide:improved means for -maintaining the efficiency of the mechanical circuit when.-

the cambers ofthe respective wings are varied simultaneously in the same direction. For convenience-.015 description the term control. cable is nsedin this specification to designate.a'member which acts'in oppo-' sition to thewind pressure during flight to control the lJOSltlOIL of ainovable traillng wire is used to designate a memberwhich V the aileron or flap in both directions.

acts in oppositiontoaficontrol cableto insure positive control of the trailing marginal portion. The term closed mechan cal circuit is. used to define an arrangement of mechanical connections between the operating and operated elements which assures positive. control inboth directions.-

23, 1919, for varying'the cambers of both;

wings simultaneously-in the same direction without interferlng With the capabllity of varying the cambers of the respective wings to aeroplanes marginal portion, and the term. balance Specification of Letters Patent. Patent d A 17 192 Application filed April 23,

1919. Serial No. 292,168.

simultaneously in reverse directions, whether the whole or only a part of the length of the trailing marginal portions of the wings be. variable, or whether said trailing marginal portions be variable as set forth in the specification accompanying my application for Us. Letters Patent, Serial No. 292,167 1 filed April 23, 1919. The means just referred to involve leading thei'espective'con trol cables, which extend in opposite direc "tions from a rotatable drum, around guide-' one control cable to be drawn upon and" the other to be relaxed, or viceversa. The

, present invention enables such means to be employed in combination with what is known-as .balance wire mechanism serv ing to complete themechanical circuit be tween the trailing marginal portions of therespective wings in such manner that when the trailing marginal portion of either wing is pulled downnby its control cable, the trailing marginal portion of the otherwing is pulled up by the balance wire; for which purpose, according to the invent-ion, not only the control cables but also the balance wires appertaining to the trailing mar-' ginal portions of the respective'wings are led around guide-pulleys the distance separating the centers of which is variable soas to relax; or draw upon the balance wires according as the control cables are drawn upon or relaxed, the balancewires performing their usual function when the cambers-of the respective wings are varied simultaneously in reverse directions.

Somewhat similar means have already been proposed in connection with an aeroplane wherein not the trailingbut the leading marginal portions of the respective wings are capable-ofhaving their inclination varied simultaneously either in reverse directions or in the same direction, atwill, by positive "action transmitted through a closed mechanical circuit. y

, One-form of the present invention is adapted to; be applied to an aer'oplaneprovided with a controlling device having a manually-rotatable drum upon which are wound, from opposite directions, the control the efiective length is variable at will; rotation of the drum causing the camber or one wing to be increased and the camber ofthe opposite wing to be reduced, whereas altera: tion in the effective length of the controlpillar will cause the cambers of both wings to be simultaneously altered in the one direction or the other according as the pillar is lengthened. or shortened. F or this purpose the balance wires appertaining to the respective trailing marginal portions of the wings are respectively led around a pair of guide pulleys rotatably mounted on the fixed portion ofthe control-pillar and, from opposite directions, around a single guide-pulley carried by the movable'portion or said control-pillar in such position relatively to the pair of guide-pulleys'that when the effective length of the control-pillar is increased the distance separating the centers'of the pair of guide-pulleys from the center or the single guide-pulley. is decreased and vice versa. Thatis to say, if the effective length of the control-pillaris increased by upward movement or that portion which carries the drum whereon are wound the control cables, the single guide-pulley is rotatably mounted on said portion ofthe pillar or on an arm carried thereby below the levelof the pair guide-pulleys which are rotatably mountedon the fixed portion of the controlpillar, so that said upward movement which serves to increasethe effective length or the control-pillar simultaneously decreases the distance separating the center of the single guide-pulley'from the centers of the pair of guide-pulleys, 'thus relaxing the balance wires to the same extent as the control cables are taken up. Inasmuch as the balance wires are not led aroundthe drum,,they only perform their usualiunctionwhen said drum is rotated to vary theicambers or the respec tive 'Wings simultaneously in reverse directions. V

The invention will be described with reference to the accompanying drawings, which illustrate diagrammatically an embodiment of the invention as applied to a sea-biplane wherein the wings of the, upper plane are extended laterally beyond those oi the lower plane, and wherein the trailingmarginal portionof each wing of the upper plane is divided intotwo parts;the inclinationsof those parts which are adjacent "to the tips of the respective wings of said planebeing variable simultaneously either in the same 4 j l the entire length of its trailing marg1nalporsimultaneously in the same direction and -,concurrently with the similar variation in the inclinations of those parts'which are adjacent to the tips, as set 'forth in thespeci fication accompanying my application for U. S. Letters Patent Serial No. 292,167; while thetrailing marginal portion of each wing of the lower plane is undivided and the inclinations of said portion olf both wings are variable {simultaneously in the same direction only, and concurrently with the similar variation in the inclinations of the trailing marginal portionsor the upper plane. I In the drawings, all of which are diagrammatic,

Figure 1 is a rear elevation of a-telescopic control pillar embodying the invention;

- Fig. 2 is a side elevation of the same;

' Fig. 3 is an elementary diagrammatic view showing the control cables for the fiaps or the upper and lower planes in full lines, the

Fig; 6 is an elementary plan View showing and ailerons; and V Fig. 7 1s a similar plan view. showing the the upper plane or the-machine, with'fiaps lower plane of the machine.

In the example illustrated, eachwing A and A of the upper plane A of the machine has the entire length of its trailing marginal portion hinged at a to the rigid main portion of the wing, and each such hinged portion is divided, at a point bnear the center of itslength, into two partswhereof thatpart B or B which is toward the outer end of the wing "constitutes an aileron (properly so called) for use in controlling the lateral sta bility of the'machi'ne as well 'asin varying. thecamber of the wing as a whole, whereas thatpart C or C whichjis toward the center of the machine constitutes what will, for the sake of distinction, behereinafter termed a flap, employed solely (in conjunction 7 tion E or E hinged at (Z to the rigid main portion of the wingfeach such flap being employed solely- (in conjunction with the flap and aileron of the corresponding-upper wing) in varying the camber of thewing as a whole;

By. the present invention theseveral' flaps and ailerons, "in whichever direction e.. downward or upward)1thejy may .be moved I about their respective hinges, are actuated positively by manual power; all the flaps C,

C and E E being movable simultaneousl 111 the same direction, downward or upwar Wvhereas'the ailerons. B, B are movable simultaneously either in the same direction as the flaps, or in directions opposite to one another independently of the movement (if any) of the flaps, at will. The means whereby these various movements are effected are, in the example illustrated, as follows.

ance wire mechanism in accordance with the present invention. As shown the control- .pillar. whereon the drum L'With its control-' ling hand-wheel is supported, is constituted by two pairs of telescopic tubes 23, 23 and 24, 24, arranged sideby side and pro vided with suitable crossheads, the drum. L" being mounted'on a spindle 25 mountedin" bearings in a crosshead 26 at the tops of the) upper or slidable portions 23,23 of the tubes so as .to be rotatable in a substantiallyvertical plane transverselyvof the machine. .A lower crosshead 27 on the portions 23, 23 of the tubes carries midway between the tubes a fixed nut 28 adapted to coact with a screwed rod 29 rotatable about asubstantially vertical axis as one with a worm wheel 30 mounted to rotatein a bearing 31 in a crosshead 32 at the tops of the lower or fixed portions 24, 24 of the-tubes, the worm wheel 30 being in mesh with a worm 33 adaptedto be rotated, in bearings formed in extensions such as 34 of the crosshead 32, on a horizontal axis transverse of the pillar and provided at one end with a crank handle 35 or the like;

The respective cables or portions of cable H Z Z which are wound around the drum L from opposite directions, extend thence downwardly and are led under a pair of guide-pulleys k rotatably mounted in a frame 36, constituting a crossheadfat the bottoms of the portions 24,24 of the tubes,

beyond which the cables Z, l are divided at' points 19 and 19* (Fig. 3) into two branches which are respectively led around stationary guide-pulleys 20, 20* (Fig. 3) to each one of pairs of levers 19?,6 fixed to the respective ailerons B B and adapted to control the position of'the same The respective cables 11, 11*, which are connected with each one of pairs of levers e 6 fixed to the lower flaps E E said flaps E E being in turn connected by pairs of cables or struts 0e, 0e and ce*, 06* to the flaps andC respectively are'attached to the crosshead' 27 or an-arm 37 projecting rearwardly' therefrom and extend thence downwardly and arezled under the pair of guideepulleys lo and 7 1 respectively, and

' thence around stationary guide-pulleys 13,

13* beyond which the cables 11 and 11* are divided at points 12 and 12* into two branches which are: respectively led around stationary guide-pulleys".13 and-13*to.the

levers e and e V 1 The respective cables 1 Z which are connected with each one of pairsof levers b -*,fb fixed tothG aIlGI'OIIS B B respectively, are wound from opposite directions around the guide-pulley L* rotatably mounted in the lower ends 'ofjrods 42 42 which extend: downwardly fromthecrosa head 27, thence the respective cables Z *,l. areled upward and. over guide-pulleys 43 43 rotatably mounted inkdownward extensions 44 ,44 of the frame 36, thence outwardly and around stationary guide-pulleys 22*, 22 beyond which the cables 11*, Z are divided at points 21*, 21 into two branches which are respectively led around stationary guide-pulleys 22*, 22 to the levers 72 12 The respective cables 14, 14* which are connected with each? one of pairs of levers c i 0 fixedtothe flaps C 0 respectively as hereinbefore. set. forth, are connectedwith arms 45, 45* projecting outwardlyfrom and carried by the lower ends ofthe rods 42 42? aforesaid, and arethence led upward and over guide-pulleys 46, 46* (behind the pulleys43 43 in Fig. 1) .rotatably mounted in the downward .extensions244 44 of the frame 36 and thence outwardly and around stationary guide-pulleys 16, 16* beyond.

which they are divided at points 15, 15* into two branches which are respectively led around stationary guide-pulleys 16, 16* to the leversc 0 Y On the one hand byrevolving the drum L' to draw upon the cable Z and relax the cable Z the cables Z andl f will be simultaneously drawn upon and relaxed respectively, the pull on the cable Z will depress the starboard, aileron B the pull on the cable 2 will'raise the port aileron B the concurrent relaxation of the cables Z and 1 permitting respectively the depression of the aileron B and the raising of the aileron B whereas,

on the other hand, revolving the drum L to drawupon the cable Z and relax the cable 7 l the cables Z and Z will besimultaneously drawn upon and relaxed respectively, the pull on the cable Z? will depressthe port aileron 13*, the pull-on the cable 1 will'raise laxation of the cables Z and Z permitting respectively the depression of the aileron B and the raising of the aileron B the starboard aileron B the concurrent re- During either of these operations the '7 cables 11, 11* and 14, 14* are unaffected.

raised together with the pulley L* and the 1 arms 45, 45* thus relaxing the cables 11*, 1 and 14, 14* respectively andpermitting the depressionof said ailerons and flaps where as if, on the other hand, the crank handle' be turned to decrease the effective length of the telescopic eontrolr'pillar, the drum Land the crosshead 27, will be lowered as one to-i gether with the rods 42 42 the pulleyL* and the arms 45, 45*, and the cables Z, Z and 14,14* will be simultaneously drawn uponto raise theailerons B B and the flaps C C? respectively; 7 At the same time the cables Z Z andthe cables 11, 11* Wil-l'be relaxed and permit the raising of said aile rons and flaps.

It will thus'b'e seen thatthe mechanical circuits are complete between the starboard and port ailerons B and B and between the starboard flaps. C E and the portflaps vC E both as regards simultaneous movement of the respective aileronsin reverse directions respectively" and as regards.simultaneous movement of the respective ailerons in the same'direction concurrently with the corresponding movement of the flaps C E and Gfi E as hereinbefore set forth.

It will be. obvious that'in all'cases the ar- 7 rangement should be such that the extent to which any 'controlcable is drawn uponfor relaxed should. be as nearly as possible exactly-equal to; the EeXtent to which the coacting but opposed cable. (which completes, I or assists in completing, the, mechanical circuits between the'parts 'controlled byisaid cables) is relaxed. or drawn upon.

I-claim a In, an aeroplane whereof the wings have trailing marginal portionsflof variable inclination, control cables, 'a control-pillar having a] fixed section and a movable sec-. tion, means for-varying the effective length of the control-pillar, a .manuallyso'perable drum mounted to rotate on the movable'section of said cOntroLpillar, said control cables being connected with the trailing marginal portions of the respective wings and wound from: opposite directions upon said manually-operable"drum, balance w res, apair 'ofguide-pulleysmountedon said fixed section of the control-pillar, 'a :single guidep'ulley carried by said movable: section of the cont'rohpillar, said balancezwires beingcon-j nected with the trailing marginal portions of the :respective :wingsand led around said-v pair of guide-pulleys andled from oppo-v site directions around. said single guidepulley, said single guide-pulley being mounted on said movable section :1n' a posi tion relatively :to said pair :of guide-pulleys to decrease the distance 7 separating; the centers of thepair of guide-pulleys from the vcenter of the single guide-pulley whenjthe effective length of the control-pillar is increased, and vice versazyq 1 CHARLES RICHARD FAIRE Yi-l 

